An Investigation of Corner Separation within a Thrust Augmenter Having Coanda Jets.

Abstract

An investigation was conducted to determine the way separation develops in the corners of thrust augmenter wings, having Coanda jets. Hot film surface sensors and pressure transducers were used, and the results indicated that separation on the test augmenter began at a corner very close to the augmenter exit and then rapidly proceeded upstream. Measurements of the velocity and pressure fields in the corner region indicated that a modified form of the Stratford criterion could be used to predict the onset of separation. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1977
Accession Number
ADA052131

Entities

People

  • Milton R. Seiler

Tags

Communities of Interest

  • Sensors
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aspect Ratio
  • Boundary Layer
  • Computer Programs
  • Corporations
  • Dual Channel
  • Fluid Dynamics
  • Layers
  • Mach Number
  • Measurement
  • Molecular Dynamics
  • Pressure Distribution
  • Pressure Gradients
  • Pressure Measurement
  • Pressure Transducers
  • Static Pressure
  • Thrust Augmentation
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Mechanics and Fluid Dynamics.